CN112649173A - Return flow type wind tunnel device for simulating low-pressure low-density dust storm environment of mars - Google Patents
Return flow type wind tunnel device for simulating low-pressure low-density dust storm environment of mars Download PDFInfo
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- CN112649173A CN112649173A CN202011629687.7A CN202011629687A CN112649173A CN 112649173 A CN112649173 A CN 112649173A CN 202011629687 A CN202011629687 A CN 202011629687A CN 112649173 A CN112649173 A CN 112649173A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
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Abstract
The invention provides a backflow type wind tunnel device for simulating a low-pressure low-density dust storm environment of mars, which comprises a backflow type wind tunnel, an ejector and an ejector, wherein the backflow type wind tunnel comprises a stable section, a contraction section, a test section, a first diffusion section, a second diffusion section, a mixing section, a third diffusion section and a large-angle diffusion section which are sequentially communicated, a first corner is communicated between the first diffusion section and the second diffusion section, a second corner is communicated between the second diffusion section and the mixing section, a third corner and a fourth corner are sequentially communicated between the third diffusion section and the large-angle diffusion section, a corner guide sheet is arranged in each corner, the ejector is arranged in the mixing section, and the ejector is arranged in the contraction section. According to the invention, the ejector is combined with the backflow type wind tunnel, the wind speed required by the test section can be achieved by small inlet pressure of the ejector, the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the cost of vacuumizing is reduced by adopting a mode of combining a large contraction ratio and a large-angle diffusion section.
Description
Technical Field
The invention belongs to the field of ground simulation of deep space exploration space environment, and particularly relates to a backflow type wind tunnel device for simulating a low-pressure low-density dust storm environment of a mars.
Background
The Mars wind tunnel is a simulation device developed aiming at extreme environment of Mars, the Mars of China has been launched in the first day, but aiming at the Mars vehicle in the first day, the wind-heat simulation of low wind speed can be carried out only by utilizing the prior art, for the Mars environment, the most obvious is low pressure, high wind speed and sand dust environment, so that a wind tunnel capable of simulating the Mars low pressure and high wind speed sand dust environment is necessarily designed, because the size of the Mars vehicle is very large, the size of a required test section is also very large, for a linear wind tunnel, a large vacuum cabin is needed outside to finish the formation of wind speed, because the size of the wind tunnel is too large, the volume of the vacuum cabin is too large, in order to generate low pressure environment, a vacuum pump set is needed to be used for vacuumizing, the large vacuum cabin consumes a large amount of time for vacuumizing, and for a backflow type wind tunnel, the vacuum cabin is not needed, the wind speed can be generated by the self-body, the volume is small, and the vacuumizing cost is low. For wind speed simulation, a fan or an ejector mode is usually adopted, but the fan is difficult to reach high wind speed in a low-pressure environment, for a linear type ejection type wind tunnel, although the high wind speed can be reached, the principle is that the ejector is used for ejecting high-pressure gas, so that the ambient pressure is reduced, the wind speed is formed due to pressure difference because the pressure of a test section is high, but the mass flow of the gas passing through the test section is only the mass flow of the ejected gas, and the gas coming out of the ejector is directly extracted, so that the efficiency is low, too much gas is consumed to reach the high wind speed, and the efficiency is necessary to be improved.
Disclosure of Invention
In view of the above, the invention aims to provide a backflow type wind tunnel device for simulating a low-pressure low-density dust storm environment of mars, which utilizes an ejector to perform a mode of combining driving with a backflow type wind tunnel, so that the wind speed required by a test section can be achieved by small inlet pressure of the ejector, and the mode of combining a large contraction ratio and a large-angle diffusion section is adopted, so that the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the cost of vacuumizing is reduced.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a backflow type wind tunnel device for simulating a Mars low-pressure low-density dust storm environment comprises a backflow type wind tunnel, an ejector and an ejector, wherein the backflow type wind tunnel comprises a stabilizing section, a contraction section, a test section, a first diffusion section, a second diffusion section, a mixing section, a third diffusion section and a large-angle diffusion section which are sequentially communicated, a first corner is communicated between the first diffusion section and the second diffusion section, a second corner is communicated between the second diffusion section and the mixing section, a third corner and a fourth corner are sequentially communicated between the third diffusion section and the large-angle diffusion section, a corner flow guide sheet is arranged in each corner, the ejector is arranged in the mixing section, the inlet section area of the large-angle diffusion section is smaller than that of the outlet section, the diffusion angle of the large-angle diffusion section is 15 degrees, the contraction ratio of the contraction section is 12, the diffusion angles of the first diffusion section, the second diffusion section and the third diffusion section are all 6-8 degrees.
Furthermore, the third diffusion section is arranged opposite to the large-angle diffusion section and the stable section area, and the third corner and the fourth corner are symmetrically arranged.
Furthermore, an anti-separation net is arranged in the large-angle diffusion section.
Further, a honeycomb device and a gauze are arranged in the stabilizing section, and the honeycomb device is arranged close to the inlet of the stabilizing section.
Furthermore, the stabilizing section is a pipeline with a uniform cross section, and the cross section of the stabilizing section is square.
Furthermore, the ejector comprises a pressure chamber and a plurality of ejection nozzles, and a plurality of nozzles are uniformly arranged on each ejection nozzle.
Further, the ejector is communicated with an air source system, the second diffusion section is communicated with a vacuum system, the vacuum system is communicated with a vacuum secondary buffer tank, and a wind speed simulation system is arranged between the air source system and the ejector.
Further, the ejector is communicated with a sand and dust system through a gas pipe, the sand and dust system is supplied with gas through a gas source system, the height of the ejector is overlapped with the central line of the wind tunnel, the ejector is arranged in the countercurrent direction, and the ejector is far away from the inlet of the test section.
Furthermore, the sectional area of an outlet of the test section is larger than that of an inlet, and the four surfaces of the hole wall are respectively diffused by 0.50 degrees along the airflow direction.
Further, an observation window is arranged on the side wall of the test section.
Compared with the prior art, the backflow type wind tunnel device for simulating the low-pressure low-density dust storm environment of the mars has the following advantages:
the pressure of the device is continuously adjustable between 100-1500Pa, the wind speed is continuously adjustable between 0-180m/s, and the sand concentration is 0.1-1g/cm3The continuously adjustable Mars backflow type wind tunnel capable of simulating the sand dust environment greatly reduces the cost of vacuumizing, improves the ejection efficiency of the ejector and has high economical efficiency.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of a backflow type wind tunnel device for simulating a low-pressure low-density dust storm environment of a mars according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a combination of a recirculation type wind tunnel device and related systems for simulating a Mars low-pressure low-density dust storm environment according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an ejector nozzle of the ejector.
Description of reference numerals:
1-a honeycomb device, 2-a gauze, 3-a stable section, 4-a contracted section, 5-a test section, 6-a first diffusion section, 7-a first corner, 8-a first corner guide vane, 9-a second diffusion section, 10-a second corner, 11-a second corner guide vane, 12-a pressure chamber, 13-an ejector, 14-a mixing section, 15-a third diffusion section, 16-a third corner, 17-a third corner guide vane, 18-a fourth corner guide vane, 19-a fourth corner, 20-a large-angle diffusion section, 21-a separation prevention net, 22-an ejector, 23-an air pipe, 24-an injection nozzle, 25-an air source system, 26-a sand dust system, 27-a vacuum system and 28-a vacuum secondary buffer tank, 29-wind speed simulation system.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-3, a backflow type wind tunnel device for simulating a low-pressure low-density dust storm environment of mars comprises a backflow type wind tunnel, an ejector 13 and an ejector 22, wherein the backflow type wind tunnel comprises a stabilizing section 3, a contracting section 4, a testing section 5, a first diffusion section 6, a second diffusion section 9, a mixing section 14, a third diffusion section 15 and a large-angle diffusion section 20 which are sequentially communicated, a first corner 7 is communicated between the first diffusion section 6 and the second diffusion section 9, a second corner 10 is communicated between the second diffusion section 9 and the mixing section 14, a third corner 16 and a fourth corner 19 are sequentially communicated between the third diffusion section 15 and the large-angle diffusion section 20, a corner deflector is arranged in each corner, the ejector 13 is arranged in the mixing section 14, the ejector 22 is arranged in the contracting section 4, and the inlet cross-sectional area of the large-angle diffusion section 20 is smaller than the outlet cross-sectional area, the diffusion angle of the large-angle diffusion section 20 is 15 degrees, the contraction ratio of the contraction section 4 is 12 degrees, and the diffusion angles of the first diffusion section 6, the second diffusion section 9 and the third diffusion section 15 are all 6 degrees.
The third diffusion section 15 is arranged opposite to the large-angle diffusion section 20 and the stable section 3, and the third corner 16 and the fourth corner 19 are symmetrically arranged.
A honeycomb device 1 and a gauze 2 are arranged in the stabilizing section 3, and the honeycomb device 1 is arranged close to the inlet of the stabilizing section 3. The honeycomb device 1 has the functions of dividing the incoming flow of the stable section, reducing the separation and divergence of the flow and improving the flow characteristic of the outlet of the stable section. The gauze 2 has the function of reducing the turbulence of airflow, is very thin in the wind tunnel, and divides a larger vortex into small vortices so as to be beneficial to attenuating the turbulence.
The ejector 13 comprises a pressure chamber 12 and nine ejector nozzles 24, the nine ejector nozzles 24 are arranged in parallel at equal intervals, and nine nozzles are uniformly formed in each ejector nozzle 24.
The ejector 14 is communicated with an air source system 25, the second diffusion section 9 is communicated with a vacuum system 27, the vacuum system 27 is communicated with a vacuum secondary buffer tank 28, and a wind speed simulation system 29 is arranged between the air source system 25 and the ejector 14.
The ejector 22 is communicated with a sand and dust system 26 through a gas conveying pipe 23, the sand and dust system 26 is supplied with gas through a gas source system 25, the height of the ejector 22 is overlapped with the central line of the wind tunnel, the ejector 22 is arranged in the reverse flow direction, and the ejector 22 is far away from the inlet of the test section. The wind-sand mixture sprays sand dust to the inside of the wind tunnel through the gas transmission pipe and the spray pipe, the sand dust is sprayed more uniformly by adopting a reverse spraying mode, and the spray pipe adopts a Venturi ejector.
For test section 5, we used a square cross section, with the following advantages:
firstly, for a mars aircraft yaw test, a wind tunnel bottom plate and a model-balance system are often required to rotate together, and the bottom plate with a square section is flat, so that the requirement can be met.
Secondly, because the bottom surface is a plane, the model is convenient to assemble and disassemble for the air inlet hole of the experimenter.
The side wall is flat, so that the observation window is convenient to install, and observation experiments and the like are facilitated.
Flat sidewalls allow half model experiments.
In the closed test section, the thickness of the boundary layer of the wall surface in the flow direction is gradually increased, so that the cross section of the flow stream is gradually reduced, the flow speed is continuously increased, and a negative static pressure gradient (pressure is gradually reduced) is generated along the axial direction. This causes the model to experience an additional drag, known as horizontal buoyancy, which is not available for atmospheric flight, and is eliminated by the cross-sectional area of the outlet of the test section 5 being greater than the cross-sectional area of the inlet and diffusing 0.50 ° along each side of the wall in the direction of the airflow.
The diffuser section is used for converting the kinetic energy of the airflow into pressure energy. Since the wind tunnel loss is proportional to the flow velocity raised to the third power, the velocity of the air flow passing through the test section should be reduced as much as possible to convert kinetic energy into pressure energy. However, deceleration is necessarily accompanied by losses, i.e., the kinetic energy cannot be entirely converted into pressure energy. According to the principle of minimum loss, the diffusion angle of the diffusion section is designed to be 6 degrees, and the section of the diffusion section is square.
The function of the constriction 4 is to accelerate the gas flow to the speed required for the experiment. The contraction ratio of the wind tunnel is improved, and the method is beneficial to the uniformity of the air flow of the test section and the reduction of the turbulence degree. Therefore, a large contraction ratio is adopted, a large-angle diffusion section 20 is additionally arranged in front of the stable section in order to increase the contraction ratio without increasing the size of the wind tunnel, separation prevention nets 21 are arranged in the large-angle diffusion section 20 in order to prevent separation caused by a large diffusion angle, and the number of layers of the nets is determined by the size of the diffusion angle.
The stabilizing section 3 is typically a constant section pipe. The downstream is connected with the contraction section 4, so the area size of the contraction section depends on the requirement of the contraction ratio of the wind tunnel. If the cross-sectional shape of the stabilizing section 3 is similar to that of the test section, the constriction section can be made simpler. The stabilizing section is square.
The corner is an important component of a back-flow type wind tunnel. The total loss of airflow at the four corners may be 40-60% of the total loss of the wind tunnel. The flow is easily separated when passing through corners, and many vortices occur, thus making the flow uneven or pulsating. Corner baffles must therefore be provided at the corners in order to prevent separation and improve flow.
The ejector provides a power source for the air speed of the testing section of the Mars dust cabin. The ejector is installed on the mixing section and mainly comprises a pressure chamber and an ejection spray pipe, the gas ejected by the ejection spray pipe is mixed with the gas to be ejected in the mixing section, the pressure chamber is connected with a gas supply pipeline controlled by a valve, and the pressure chamber is used for providing stable pressure for the ejection nozzles and ensuring that the outlet airflow states of all the nozzles are kept consistent.
The air source system 25, the sand-dust system 26, the vacuum system 27, the vacuum secondary buffer tank 28 and the wind speed simulation system 29 mentioned in the present application are all existing systems, and are not described in detail in the present application.
As shown in fig. 2, which is a diagram of a wind tunnel system, firstly, the wind tunnel is evacuated by the vacuum system and directly discharged to the atmosphere, and the vacuum secondary buffer tank 28 is also evacuated until the pressure is reduced to a specified pressure. The air supply valve of the air source system 25 is opened, the air source system 25 provides stable pressure air flow to the air speed simulation system 29, the air flow reaches the spray pipe through the ejector 13 and is connected with the air pipe, the air flow is rapidly sprayed out through the ejector spray pipe 24, the air forms suction in a rapid expansion mode, the air flow at other positions of the air hole can be sucked in and together with the ejection air flow, the air flow passes through the test section 5, when the pressure reaches the designated pressure, redundant air is discharged out of the vacuum secondary buffer tank 28 through the vacuum system 27, the air speed simulation system 29 adjusts the air speed, the air speed of the test section 5 reaches the preset air speed, the sand dust system 26 starts to work, the air source system 25 carries sand dust with certain concentration to be sprayed into the air hole, the spraying amount is adjusted through the sand dust system 26 until the designated sand dust concentration is reached, the test is started.
The ejector is optimized in a mode of combining driving with a backflow type wind tunnel, so that when the environmental pressure is 1000Pa, the air speed of a test section can exceed 180m/s only by 70000Pa of the inlet pressure of the ejector, and the mode of combining a large contraction ratio with a large-angle diffusion section is adopted, so that the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the cost of vacuumizing is reduced.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A backflow type wind tunnel device for simulating a Mars low-pressure low-density dust storm environment is characterized in that: the device comprises a backflow type wind tunnel, an ejector (13) and an ejector (22), wherein the backflow type wind tunnel comprises a stable section (3), a contraction section (4), a test section (5), a first diffusion section (6), a second diffusion section (9), a mixing section (14), a third diffusion section (15) and a large-angle diffusion section (20) which are sequentially communicated, a first corner (7) is communicated between the first diffusion section (6) and the second diffusion section (9), a second corner (10) is communicated between the second diffusion section (9) and the mixing section (14), a third corner (16) and a fourth corner (19) are sequentially communicated between the third diffusion section (15) and the large-angle diffusion section (20), a corner flow guide sheet is arranged in each corner, the ejector (13) is arranged in the mixing section (14), and the ejector (22) is arranged in the contraction section (4), the inlet section area of the large-angle diffusion section (20) is smaller than the outlet section area, the diffusion angle of the large-angle diffusion section (20) is 15 degrees, the contraction ratio of the contraction section (4) is 12, and the diffusion angles of the first diffusion section (6), the second diffusion section (9) and the third diffusion section (15) are all 6-8 degrees.
2. The wind tunnel device of claim 1, wherein the wind tunnel device is a wind tunnel device for simulating a low pressure and low density dust storm environment of mars: the third diffusion section (15) is arranged opposite to the large-angle diffusion section (20) and the stable section (3) in area, and the third corner (16) and the fourth corner (19) are symmetrically arranged.
3. The wind tunnel device of backflow type for simulating low-pressure and low-density dust storm environment of mars according to claim 1 or 2, wherein: an anti-separation net (21) is arranged in the large-angle diffusion section (20).
4. The wind tunnel device of claim 3, wherein said wind tunnel device is a tunnel device for simulating low pressure and low density dust storm environment of Mars: a honeycombed device (1) and a gauze (2) are arranged in the stabilizing section (3), and the honeycombed device (1) is arranged close to the inlet of the stabilizing section (3).
5. The wind tunnel device of recirculation type for simulating low pressure and low density dust storm environment of Mars according to claim 1, 2 or 4, wherein: the stabilizing section (3) is a pipeline with a uniform cross section, and the cross section is square.
6. The wind tunnel device of claim 5, wherein said wind tunnel device is a tunnel device for simulating low pressure and low density dust storm environment of Mars: the ejector (13) comprises a pressure chamber (12) and a plurality of ejector nozzles (24), and a plurality of nozzles are uniformly arranged on each ejector nozzle (24).
7. The wind tunnel device of backflow type for simulating low-pressure and low-density dust storm environment of mars according to claim 1 or 2, wherein: the ejector (14) is communicated with an air source system (25), the second diffusion section (9) is communicated with a vacuum system (27), the vacuum system (27) is communicated with a vacuum secondary buffer tank (28), and a wind speed simulation system (29) is arranged between the air source system (25) and the ejector (14).
8. The wind tunnel device of claim 7, wherein said wind tunnel device is a tunnel device for simulating low pressure and low density dust storm environment of Mars: ejector (22) are through gas-supply pipe (23) and sand and dust system (26) intercommunication, sand and dust system (26) are by air supply system (25) air feed, the height and the coincidence of wind-tunnel central line of ejector (22), and adopt the countercurrent direction to arrange, experimental section entry is kept away from in ejector (22).
9. The wind tunnel device of backflow type for simulating low-pressure and low-density dust storm environment of mars according to claim 1 or 2, wherein: the sectional area of the outlet of the test section (5) is larger than that of the inlet, and the four surfaces of the hole wall are respectively diffused by 0.50 degrees along the airflow direction.
10. The wind tunnel device of claim 9, wherein said wind tunnel device is a tunnel device for simulating a low pressure and low density dust storm environment of mars: an observation window is arranged on the side wall of the test section (5).
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| CN202011629687.7A CN112649173B (en) | 2020-12-30 | 2020-12-30 | Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment |
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| CN202011629687.7A CN112649173B (en) | 2020-12-30 | 2020-12-30 | Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment |
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| CN113390603A (en) * | 2021-06-17 | 2021-09-14 | 哈尔滨工业大学 | Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof |
| CN115290287A (en) * | 2022-10-08 | 2022-11-04 | 中国空气动力研究与发展中心低速空气动力研究所 | High-altitude low-density wind tunnel test system and method and wind speed measurement method |
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| CN112649173B (en) | 2023-08-11 |
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